Aerodynamic Characterization of HEXAFLY Scramjet Propelled Hypersonic Vehicle

Pezzella, Giuseppe; Marini, Marco; Cicala, Marco; Vitale, Antonio; Langener, Tobias; Steelant, Johan

doi:10.2514/6.2014-2844

Cited by 20 publications

(8 citation statements)

References 10 publications

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“…Several design iterations were performed by CIRA to assure that this could be achieved [8]. Early on in the design process, it became clear that lateral directionality could be achieved by means of fixed rudders, but that the longitudinal stability required active control by means of ailerons.…”

Section: B Flight Control Analysis and Layoutmentioning

confidence: 98%

Conceptual Design of the High-Speed Propelled Experimental Flight Test Vehicle HEXAFLY

Steelant¹,

Langener²,

Matteo³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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A concise overview of the overall layout of an experimental powered high-speed flight vehicle including its subsystems is given. A mission scenario, the different flight segments and events to which the payload is exposed are described and justified. This allowed the definition of the aero-thermo-mechanical loads required to conceptually design all elements on board of the vehicle. The final vehicle configuration could achieve the different mission objectives. In particular an aero-propulsive balance, i.e. thrust ≥ drag and lift ≥ weight, could be established at a cruise Mach number of M = 7.4 on the basis of a hydrogen powered scramjet engine while guaranteeing a good aerodynamic efficiency L/D ≥ 4 in a stable, trimmed and controlled way. The experimental combustion campaign could last for at least for 3s up to 9s pending on the finally obtained flight level. This test time is very valuable as it is about 3 orders of magnitude higher of what can be tested in European ground facilities. The vehicle made maximum use of databases, expertise, technologies and materials elaborated in previously EC co-funded projects ATLLAS I & II and LAPCAT I & II.Based on this conceptual design, the consortium has arrived at a key point where they feel comfortable to go to the next step in establishing a detailed design of the vehicle and the preparation of the launch vehicle and flight campaign.

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Section: B Flight Control Analysis and Layoutmentioning

confidence: 98%

Conceptual Design of the High-Speed Propelled Experimental Flight Test Vehicle HEXAFLY

Steelant¹,

Langener²,

Matteo³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…To provide a high lift-to-drag ratio and a low specific fuel consumption during a long haul flight it was developed a waverider type fuselage-wing integration with leeward positioned engine. 6,11 The leeward surfaces of the fuselage and the wing are aligned on the flight velocity direction and a main part of the lift is generated by the windward side of the cruiser (Fig. 7).…”

Section: High-speed Flying Vehicle With Hypergeometrically Profilementioning

confidence: 99%

High-speed flying vehicle with hypergeometrically shaped windward aerodynamic surface

Takovitskii¹

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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This work discusses the problem of reducing the drag due to lift at high-speed flight conditions. To accelerate the optimization algorithm convergence and to study characteristic features of the optimal delta wing the procedure of the geometry parameters system selection is developed within the framework of the linear theory. It is established that the hypergeometrical directrix of the wing describes near to optimum aerodynamic shape and corresponds to a superelliptical distribution of the local angle of attack over the wing span. Differences between the results of the theoretical studying and the direct numerical optimization based on the Euler's equations are analyzed. Configuration of the high-speed flying vehicle, designed under HEXAFLY-INT project, with hypergeometrically profiled windward surface is proposed to enhance aerodynamic performance. Flow fields and aerodynamic loads numerical studying is carried out in a wide range of the Mach number. Nomenclature X = axis directed along the free stream R  = aerodynamic force velocity 2 n  = nozzle exit normal Y = axis of lift force I = flow momentum Z = lateral axis y = normalized normal coordinate M = Mach number z = normalized lateral coordinate V = free stream velocity Re = Reynolds number α = angle of attack C P = pressure coefficient N = number of elements q = pressure velocity F = objective function G = constraint function Subscripts C D = aerodynamic drag coefficient fl = flat wing C L = lift coefficient EXT = external C m = pitching moment coefficient f = mass flow rate ν = eigenvalue u = eigenvector H = Hessian matrix n = relative sweepback μ = Mach angle χ = sweep angle at the leading edge φ = perturbation velocity potential λ = Lagrange multiplier E = form parameter 2 F 1 = Gauss hypergeometric function ψ = twist angle L = fuselage length S = reference area 1 Head of Research Group, Aerodynamics Department, TsAGI, c.a.t@tsagi.ru, not a member of the AIAA Downloaded by UNIVERSITY OF ILLINOIS on October 1, 2015 | http://arc.aiaa.org |

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“…773 modes;  A 1.5% critical damping is used for all modes;  The vehicle is constrained to its base and it is excited by the acceleration spectrum by using the large mass approach;  The spectrum is applied simultaneously in radial and longitudinal direction, i.e. in turn along x and y axes and along x and z axes;  NRL summation criterion [1].…”

Section: Shock Response Spectrummentioning

confidence: 99%

“…During the last decade CIRA, the Italian Aerospace Research Centre, has been leading different research projects concerning in-flight demonstration of key technologies for re-entry systems in the framework of national and international programs [1][2][3][4]. Within the national USV (unmanned space vehicle) program [5], the USV3 project is the current driving project [6].…”

Section: Introductionmentioning

confidence: 99%

Dynamic loads evaluation for the USV3-PRIDE robotic arm qualification

Paletta¹,

Vice²,

Belardo³

2016

WIT Transactions on the Built Environment

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This paper presents the evaluation of the dynamic loads for the qualification of a robotic arm, to be installed on-board the USV3-PRIDE spacecraft. CIRA is developing a fully reusable unmanned space vehicle, code named USV3-PRIDE, to be launched by VEGA. The system is capable of orbiting, de-orbiting and gliding back to Earth with high manoeuvrability and controllability throughout all flight regimes (i.e. hypersonic re-entry, supersonic, transonic, subsonic) and performing a safe ground landing on a conventional runway by a landing gear system. Such aerospace systems could lead to the new technological frontier to master both new and innovative orbital robotic systems in the near Earth environment, as well as to explore the hypersonic flight regimes necessary to re-enter the earth from above 300 Km altitude to the ground, which represent the same flight levels of the future aerospace transportation systems. The spacecraft is equipped with a robotic arm which provides the capability to ship a payload and interface with a space tug towards the International Space Station. During ground operation and flight the spacecraft is subject to different kinds of loads, both static and dynamic. These excitations are from different origins such as operational, aerodynamics or propulsion. In particular, for the mechanical qualification of the robotic arm and the other subsystems, the dynamic environment provides for the most severe conditions in terms of local accelerations. The dynamic environment taken under consideration includes two types of dynamic analyses: Shock Response Spectrum (SRS) analysis, and Sine equivalent dynamics. SRS analysis is necessary to calculate the structural local response to shocks and to estimate the maximum dynamic response of a structure. The spacecraft is

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Aerodynamic Characterization of HEXAFLY Scramjet Propelled Hypersonic Vehicle

Cited by 20 publications

References 10 publications

Conceptual Design of the High-Speed Propelled Experimental Flight Test Vehicle HEXAFLY

Conceptual Design of the High-Speed Propelled Experimental Flight Test Vehicle HEXAFLY

High-speed flying vehicle with hypergeometrically shaped windward aerodynamic surface

Dynamic loads evaluation for the USV3-PRIDE robotic arm qualification

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